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CA2462517A1 - Carrying or guiding device for aircraft components - Google Patents

Carrying or guiding device for aircraft components Download PDF

Info

Publication number
CA2462517A1
CA2462517A1 CA002462517A CA2462517A CA2462517A1 CA 2462517 A1 CA2462517 A1 CA 2462517A1 CA 002462517 A CA002462517 A CA 002462517A CA 2462517 A CA2462517 A CA 2462517A CA 2462517 A1 CA2462517 A1 CA 2462517A1
Authority
CA
Canada
Prior art keywords
carrier
carrying
joints
guiding device
aircraft components
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CA002462517A
Other languages
French (fr)
Other versions
CA2462517C (en
Inventor
Walter A. Stephan
Hermann Filsegger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Facc AG
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of CA2462517A1 publication Critical patent/CA2462517A1/en
Application granted granted Critical
Publication of CA2462517C publication Critical patent/CA2462517C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Connection Of Plates (AREA)

Abstract

The invention relates to a carrying or guiding device (1) for aircraft components, especially for a landing flap which is arranged on an aircraft wing. The inventive device comprises a carrier (2) having an essentially U-shaped profile and essentially parallel lateral walls (3, 4). In order to produce one such device in such a way that it weighs as little as possible, has the required mechanical properties, and is as easy to produce and to assemble as possible, the carrier (2), and preferably one covering plate (20) arranged on the open side of the carrier (2), are produced from fibre reinforced plastic, especially carbon fibre reinforced plastic (CFRP). The connection between the carrier (2) and the covering plate (20) and possible connection elements (21) is preferably carried out by means of glued joints and, if necessary, additional riveted joints or screwed joints.
CA002462517A 2001-10-24 2002-09-16 Carrying or guiding device for aircraft components Expired - Fee Related CA2462517C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
ATA1690/2001 2001-10-24
AT0169001A AT410656B (en) 2001-10-24 2001-10-24 TRAG- OR GUIDE DEVICE FOR AIRCRAFT COMPONENTS
PCT/AT2002/000266 WO2003035469A1 (en) 2001-10-24 2002-09-16 Carrying or guiding device for aircraft components

Publications (2)

Publication Number Publication Date
CA2462517A1 true CA2462517A1 (en) 2003-05-01
CA2462517C CA2462517C (en) 2008-11-18

Family

ID=3688670

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002462517A Expired - Fee Related CA2462517C (en) 2001-10-24 2002-09-16 Carrying or guiding device for aircraft components

Country Status (7)

Country Link
US (1) US7011276B2 (en)
EP (1) EP1438230B1 (en)
AT (1) AT410656B (en)
CA (1) CA2462517C (en)
DE (1) DE50202945D1 (en)
ES (1) ES2240805T3 (en)
WO (1) WO2003035469A1 (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004006940B4 (en) * 2004-02-12 2009-02-26 Airbus Deutschland Gmbh Landing flap guide for aircraft
DE102005017307A1 (en) 2005-04-14 2006-10-26 Airbus Deutschland Gmbh Landing flap drive system for use in aircraft, is connected to track of landing flap which is operated by drive motor
US7249735B2 (en) * 2005-06-30 2007-07-31 The Boeing Company Translating conduit apparatus for an airplane or equipment
DE102007048449A1 (en) 2007-10-10 2009-04-23 Eads Deutschland Gmbh Lift flaps support system
DE102008028542B4 (en) * 2008-06-16 2012-07-12 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Method and apparatus for depositing a layer on a substrate by means of a plasma-enhanced chemical reaction
DE102008047793B4 (en) 2008-09-17 2017-03-30 Airbus Defence and Space GmbH Load introduction element
JP5562575B2 (en) * 2009-04-27 2014-07-30 ナブテスコ株式会社 Aircraft actuator
JP2011116147A (en) * 2009-11-30 2011-06-16 Nabtesco Corp Reaction link
JP5552340B2 (en) * 2010-03-15 2014-07-16 ナブテスコ株式会社 Actuator and link manufacturing method, actuator and link design method, actuator and link
GB201111922D0 (en) 2011-07-12 2011-08-24 Airbus Operations Ltd Leading edge rib assembly
FR2990187B1 (en) * 2012-05-07 2015-01-30 Airbus Operations Sas BEAM IN COMPOSITE MATERIAL INCORPORATING A CLOSED SECTION REINFORCEMENT
DE102014106930B4 (en) * 2014-05-16 2024-07-04 Airbus Operations Gmbh Load-bearing fairing element for a flap adjustment mechanism and aircraft with such a fairing element
EP3025955B1 (en) * 2014-11-26 2019-06-19 Airbus Defence and Space GmbH High lift system

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2112154A (en) * 1935-08-02 1938-03-22 Randolph F Hall Airplane
US4471928A (en) * 1980-08-13 1984-09-18 The Boeing Company Extendible airfoil track assembly
US4451528A (en) * 1981-03-30 1984-05-29 Ni Industries, Inc. Composite fiber reinforced member and method
US4542869A (en) * 1983-06-23 1985-09-24 Mcdonnell Douglas Corporation Flap mechanism
GB8718977D0 (en) * 1987-08-11 1987-09-16 British Aerospace Trailing edge flaps
US5171510A (en) * 1988-06-08 1992-12-15 Aerospatiale Societe Nationale Industrielle Method of producing a frame made of a composite material, especially for the fuselage of an aircraft
GB8819535D0 (en) * 1988-08-17 1988-09-21 British Aerospace Wing flap track beams for aircraft
GB9024387D0 (en) * 1990-11-09 1991-01-02 British Aerospace Carbon fibre composite wing manufacture
DE4107556C1 (en) * 1991-03-08 1992-05-14 Deutsche Airbus Gmbh, 2000 Hamburg, De
FR2679866B1 (en) * 1991-08-02 1993-11-05 Piquereau Jean Yves SMALL SIZE CARGO AIRCRAFT.
SE502781C2 (en) * 1993-08-20 1996-01-15 Transman Ab Universal beam for moving load
JP3839080B2 (en) * 1995-06-21 2006-11-01 富士重工業株式会社 Structure of fiber-reinforced composite material and manufacturing method thereof
US5788190A (en) * 1996-10-22 1998-08-04 The Boeing Company Slotted cruise trailing edge flap
US6237304B1 (en) * 1997-07-18 2001-05-29 Henkel Corporation Laminate structural bulkhead
DE1268272T1 (en) * 2000-04-05 2003-06-26 Bell Helicopter Textron, Inc. DESIGNING A HOLE IN K-SHAPE FOR A GLUED WING STRUCTURE
US6719870B2 (en) * 2000-12-15 2004-04-13 The Boeing Company Fastenerless internal support for hollow structures
JP4574086B2 (en) * 2001-09-03 2010-11-04 富士重工業株式会社 Method for manufacturing composite wing and composite wing

Also Published As

Publication number Publication date
CA2462517C (en) 2008-11-18
US20050082434A1 (en) 2005-04-21
ES2240805T3 (en) 2005-10-16
AT410656B (en) 2003-06-25
ATA16902001A (en) 2002-11-15
EP1438230A1 (en) 2004-07-21
EP1438230B1 (en) 2005-04-27
WO2003035469A1 (en) 2003-05-01
US7011276B2 (en) 2006-03-14
DE50202945D1 (en) 2005-06-02

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Legal Events

Date Code Title Description
EEER Examination request
MKLA Lapsed

Effective date: 20200916